GB822067A - Blades and blade mounting assemblies for turbines and axial flow compressors - Google Patents

Blades and blade mounting assemblies for turbines and axial flow compressors

Info

Publication number
GB822067A
GB822067A GB36749/56A GB3674956A GB822067A GB 822067 A GB822067 A GB 822067A GB 36749/56 A GB36749/56 A GB 36749/56A GB 3674956 A GB3674956 A GB 3674956A GB 822067 A GB822067 A GB 822067A
Authority
GB
United Kingdom
Prior art keywords
tongues
root
blades
blade
spacer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB36749/56A
Inventor
Leonard James Dennis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by D Napier and Son Ltd filed Critical D Napier and Son Ltd
Publication of GB822067A publication Critical patent/GB822067A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

822,067. Turbines and axial-flow compressors. NAPIER & SON Ltd., D. Oct. 28, 1957 [Nov. 30, 1956], No. 36749/56. Class 110 (3). In a blade assembly for a turbine or axialflow compressor, the blade carrying member, say the rotor, is provided with substantially axially-directed grooves to receive the blade roots, each blade is formed from sheet metal or tube to provide a hollow aerofoil portion and two root tongues extending from the concave and convex faces of the aerofoil portion, the root tongues being received in adjacent grooves in the rotor together with the root tongues of the adjacent blades. Spacer members are disposed between adjacent blades, each spacer having a projection which is received in the groove occupied by root tongues of the blades on each side of it. The turbine rotor disc 10 shown has bulb-secction grooves 11 formed in its periphery and each blade 16 has a pair of root tongues 17, 18, which are received in adjacent grooves 11, being correspondingly shaped. The root tongues 17, 18 of adjacent blades are fitted in the grooves 11 as shown in Fig. 2. Each spacer 21 has a flat upper surface shaped to correspond with the concave and convex surfaces of the blades on either side of it and has a stem 24 with a half-bulb root portion 25 which is received in a groove 11 between a pair of root tongues 17, 18, a semicylindrical key 28 being driven into the space between the root 25 and tongues 17, 18 to wedge the parts in the groove. The spacer 21 has end walls 26, 27 which blank off the spaces between the tongues 17, 18 of adjacent blades. One limb of a resilient angle-section lug may be secured to the tongue 18, the other limb of the lug engaging the under-surface of the adjacent spacer 21 whereby the vibration characteristics of the blade are modified. In a further modification, ferrules 37 are secured in the root tongues 17, 18 of each blade, and a lacing wire 39 is threaded circumferentially through the bores of the ferrules, the wire being a close fit in narrowed portions of the bores. The wire is deformed as at 40 along its length so as to locate it circumferentially. This arrangement serves to apply frictional restraint against lateral flutter. Cooling medium may be supplied to the hollow interiors of the blades through the spaces between the tongues 17. 18. Reference has been directed by the Comptroller to Specification 650,424.
GB36749/56A 1956-11-30 1956-11-30 Blades and blade mounting assemblies for turbines and axial flow compressors Expired GB822067A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB345903X 1956-11-30

Publications (1)

Publication Number Publication Date
GB822067A true GB822067A (en) 1959-10-21

Family

ID=10367519

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36749/56A Expired GB822067A (en) 1956-11-30 1956-11-30 Blades and blade mounting assemblies for turbines and axial flow compressors

Country Status (6)

Country Link
US (1) US2967043A (en)
BE (1) BE562857A (en)
CH (1) CH345903A (en)
FR (1) FR1188652A (en)
GB (1) GB822067A (en)
NL (2) NL102164C (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US9145784B2 (en) 2011-04-14 2015-09-29 Rolls-Royce Plc Annulus filler system

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
US3471127A (en) * 1966-12-08 1969-10-07 Gen Motors Corp Turbomachine rotor
US3741681A (en) * 1971-05-28 1973-06-26 Westinghouse Electric Corp Hollow turbine rotor assembly
US3801222A (en) * 1972-02-28 1974-04-02 United Aircraft Corp Platform for compressor or fan blade
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
FR2404134A1 (en) * 1977-09-23 1979-04-20 Snecma ROTOR FOR TURBOMACHINES
FR2639402B1 (en) * 1988-11-23 1990-12-28 Snecma TURBOMACHINE ROTOR WING DISC
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US5425622A (en) * 1993-12-23 1995-06-20 United Technologies Corporation Turbine blade attachment means
WO2012009482A2 (en) * 2010-07-13 2012-01-19 Nature's Energy Banc Connection mechanism for mounting blades for a wind turbine
US10633985B2 (en) * 2012-06-25 2020-04-28 General Electric Company System having blade segment with curved mounting geometry
US9243501B2 (en) * 2012-09-11 2016-01-26 United Technologies Corporation Turbine airfoil platform rail with gusset
US9650902B2 (en) * 2013-01-11 2017-05-16 United Technologies Corporation Integral fan blade wear pad and platform seal
EP2956626B1 (en) * 2013-02-12 2019-11-20 United Technologies Corporation Fan blade including external cavities
US10767498B2 (en) * 2018-04-03 2020-09-08 Rolls-Royce High Temperature Composites Inc. Turbine disk with pinned platforms
FR3080322B1 (en) * 2018-04-20 2020-03-27 Safran Aircraft Engines BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND MANUFACTURING METHOD THEREOF
CN110566282B (en) * 2019-10-24 2024-08-09 哈尔滨汽轮机厂有限责任公司 835Mm last-stage moving blade suitable for low-load working condition operation

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190815893A (en) * 1908-07-27 1909-01-28 Arthur William Cooper Improvements in Turbine Engines.
FR969413A (en) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Further training in the construction and fixing of hollow blades for gas turbines
FR998221A (en) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Improvements in the attachment of turbo-machine blades
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US9145784B2 (en) 2011-04-14 2015-09-29 Rolls-Royce Plc Annulus filler system

Also Published As

Publication number Publication date
BE562857A (en)
NL102164C (en)
FR1188652A (en) 1959-09-24
US2967043A (en) 1961-01-03
CH345903A (en) 1960-04-30
NL222612A (en)

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